CN101596938A - A kind of test system of spoiler power control unit - Google Patents
A kind of test system of spoiler power control unit Download PDFInfo
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- CN101596938A CN101596938A CNA2009100398130A CN200910039813A CN101596938A CN 101596938 A CN101596938 A CN 101596938A CN A2009100398130 A CNA2009100398130 A CN A2009100398130A CN 200910039813 A CN200910039813 A CN 200910039813A CN 101596938 A CN101596938 A CN 101596938A
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Abstract
A kind of test macro of plane spoiler power control assembly, comprise test fixture: the fixed bearing that on a base plate, is provided with load oil cylinder and measured piece accordingly, be fixed with the load oil cylinder on the load oil cylinder fixed bearing and pass through the coaxial continuous external force gauge of adapter, the measured piece fixed bearing is for being connected the horizontal loaded board on the base plate with attaching parts; Load oil cylinder fixed bearing is that horizontal riser both sides are added with gusset backwards, is laterally having a plurality of cooresponding support rod hole on loaded board and the riser, is provided with cooresponding removable strut bar and passes support rod hole and connect two bearings; Also be provided with external displacement pickup on the base plate; Electric control system: comprise signal generating module, location solution mediation feedback gain adjustment module, external sensor module and pilot control system module, signal generating module and external sensor module respectively adopt the high-precision microprocessor control of multidigit, have guaranteed signal accuracy and convenient the adjusting.
Description
Technical field
The present invention relates to the test macro of a kind of plane spoiler power control assembly (PCU), especially relate to the test macro of B777 plane spoiler PCU.
Background technology
The rear of aircraft wing is provided with spoiler, and it can swing up and down around a jointed shaft that is parallel to the wing length direction, and power resources are in an oscillating oil cylinder.Opportunity, angle and feedback speed of spoiler swing or the like wanted could determine behind the comprehensive various complicated situations, and depended on the travel displacement and the speed of oscillating oil cylinder piston.Therefore except that oscillating oil cylinder, also on oil circuit, be provided with electric hydraulic control valve, integrate and form spoiler power control assembly (PCU).
Plane spoiler PCU must be through test, test travel displacement and the speed of response of its oil cylinder under various control commands, test macro has generally comprised test fixture, various sensors and electric control system, at present, the test macro of plane spoiler PCU does not have unified standards and norms, spoiler PCU annex is finalized the design when aircraft delivery is used, and the plane spoiler of same type has the branch in inboard and the outside again, the test macro of each spoiler is at the specific while design-calculated of specific spoiler PCU, design time very early, the general only suitable single model hydraulic services of test fixture, test fixture adopts corresponding application specific architecture, universality is poor, does not catch up with the development of modern mechanical technology, and also will carry out complicated school dress and debugging in the use.
Summary of the invention
Purpose of the present invention, just provide a kind of universality good plane spoiler (especially B777 spoiler) PCU test macro, can test B777 inboard and outside spoiler PCU annex, and can also change the test fixture accessory that matches with PCU easily and carry out the test of other plane spoilers PCU.
The technical solution adopted for the present invention to solve the technical problems is:
The test macro of a kind of plane spoiler power control assembly (PCU) comprises test fixture and electric control system, it is characterized in that:
Described test fixture structure is: the fixed bearing that is provided with load oil cylinder and measured piece on a base plate accordingly, be fixed with the load oil cylinder on the load oil cylinder fixed bearing and pass through the coaxial continuous external force gauge of adapter, the measured piece fixed bearing is for being connected the horizontal loaded board on the base plate with attaching parts; Described load oil cylinder fixed bearing is that horizontal riser both sides are added with gusset backwards, is laterally having a plurality of cooresponding support rod hole on loaded board and the riser, is provided with cooresponding removable strut bar and passes support rod hole and connect two bearings; Also be provided with external displacement pickup (LVDT) on the base plate;
Described electric control system comprises signal generating module, location solution mediation feedback gain adjustment module, external sensor demodulation module, pumping signal, command signal and external sensor module all adopt the high-precision microprocessor control of multidigit, have guaranteed signal accuracy and convenient the adjusting.
Described external sensor data acquisition module comprises first microcontroller (numbering 1), two paths of data acquisition channel (numbering 2), load and displacement show (numbering 3), five parts of power supply (numbering 4) and supply terminals (numbering 5): data acquisition channel with sensor acquisition to signal give first microcontroller (STC12C5410AD), first microcontroller includes the analog to digital conversion unit, the two-way analog signal conversion can be become digital signal and through giving load after the computing and the displacement display circuit shows by the analog to digital conversion unit.
Is described signal generating module made of pumping signal generation and adjustment module, command signal generation and adjustment module again? mainly comprise: second microcontroller (numbering 6), keyboard (numbering 7), digital to analogy conversion and push-pull output circuit (numbering 8), s-f and amplitude display circuit (numbering 9) and power supply (numbering 10) and terminals (numbering 11): second microcontroller (dsPIC30F4012) is after obtaining the control signal of keyboard, the one side output data is to analogue to digital conversion and recommend output, on the other hand with data feed signals frequency and amplitude display part;
Analogue to digital conversion with recommend output and comprise two data latches 74HL373, two analog-digital chip AD7846JN, a slice amplifier LM324 and recommend output triode 5551 and 5401,74HL373 will latch from the data of microcontroller and supply with AD7846JN; Output amplitude reference voltage after a slice AD7846JN digital to analogy conversion wherein, after amplifier LM324 conversion, form positive and negative magnitude references voltage again and supply with another sheet AD7846JN, the output of another sheet AD7846 is desired signal type, and (this module can produce sine, the trigonometric sum square wave), through after the utmost point recommend and amplify back output;
S-f and amplitude display part comprise that two LED chip for driving MC14489BP and 5 highlighted LED.MC14489 obtain the microcontroller data through serial port, send LED to show the frequency and the amplitude of signal then.
Described pilot control system comprises: servovalve command signal and location bias, servovalve feedback and adjusting and signal operation and three parts of driving output, during open loop control, give the command signal input control signal? deliver to the signal input and drive output with the servovalve location bias behind overregulate, servovalve drives exports to servovalve; During closed loop control, the servovalve feedback signal is reconciled the back through filtering and is given the signal input and drive output with above-mentioned two paths of signals, has introduced the servovalve feedback signal here and has formed closed loop control system.
In servovalve command signal and the location bias: order biasing (numbering 12) output forms command signal output with command signal input two paths of signals after op amp LM248N stack, and servovalve location bias (numbering 14) is the same as with order biasing (numbering 12) op amp output.
Servovalve feedback with regulate: the servovalve feedback signal forms the actv. feedback signal after through the servovalve filtering is made up of amplifier LM248N and adjusting (numbering 15) circuit, feedback signal links to each other with open/close control (numbering 16), opening/the closed loop state of switch S 201 control system, when closed loop, feedback signal is regulated the signal stack of (numbering 18) output with location bias through position amplitude adjusted (numbering 17), finally formed position signal output, simultaneously the variation tendency of VM2 needle dc voltmeter indicator signal;
During signal operation is exported with driving: the servovalve location bias, the servovalve command signal, servovalve position signal three road signals are input to signal operation and adjusting (numbering 20) circuit, give next stage servovalve gain-adjusted (numbering 21) after regulating through stack and amplification.Deliver to servovalve after the servovalve gain-adjusted again and drive (numbering 22) circuit.Servovalve drives to be made up of amplifier LM248N and pliotron, finally forms servo valve drive signal.The variation tendency of the drive signal of mAM pointer-type amperemeter/ammtr indication simultaneously.
During test, measured piece is installed on the loaded board of test fixture, the electric connection of measured piece is connected with electric control system with displacement pickup joint, external force gauge electric connection and external displacement pickup electric connection, adding the hydraulic pressure load tests, required electrical quantity requires behind signals such as microcontroller adjusted pumping signal, command signal, offset signal, feedback amplitude according to the measured piece model, carries out open and close ring control test.
Beneficial effect of the present invention: because fixed bearing is provided with removable strut bar, dismounting strut bar as the case may be, the test fixture bottom deformation is excessive when having avoided the heavy load when detection spoiler PCU oil cylinder; By changing the measured piece loaded board, can finish the test of the interior outside spoiler PCU assembly of B777, structure is consistent with principle and the requirement of annex manual of maintenance, the convenient adjusting and test.Commonality is good, is convenient to expanded function.
Description of drawings
The present invention is described in further detail below in conjunction with the drawings and specific embodiments.
Fig. 1 is a test system structure schematic diagram of the present invention;
Fig. 2 is the test fixture structure assembling scheme drawing of test macro embodiment of the present invention;
Fig. 3 is the birds-eye view of Fig. 2;
Fig. 4 is electric control theory figure;
Fig. 5 is command signal and pumping signal block diagram;
Fig. 6 is an external sensor data acquisition functional block diagram;
Fig. 7 external sensor data acquisition module circuit diagram;
Fig. 8 is the signal generating module circuit diagram;
Fig. 9 is the pilot control system circuit diagram.
Among the figure: 1-base plate, 2-load oil cylinder, the horizontal riser of 3-, 31-gusset, 4-strut bar, 5-adapter, 6-jockey pulley formula tension-compression sensor, 7-LVDT adapter plate, 8-U type folder, 9-install riser, 10-measured piece, 11-oil cylinder fixed bearing, 12-measured piece fixed bearing.
The specific embodiment
To shown in Figure 9, the test macro of plane spoiler power control assembly of the present invention (PCU) comprises test fixture and electric control system as Fig. 1.
Referring to Fig. 2, Fig. 3, the structure of test fixture is: the fixed bearing 12 that is provided with load oil cylinder fixed bearing 11 and measured piece spoiler power control assembly 10 on base plate 1 accordingly, load oil cylinder fixed bearing 11 is that a horizontal riser 3 both sides are added with gusset 31 backwards, be fixed with load oil cylinder 2 on it, be connected with coaxial external force gauge 6 by adapter 5, also be provided with Linear displacement transducer 7 on the base plate 1, measured piece fixed bearing 12 is for being connected the horizontal loaded board 9 on the base plate 1 with attaching parts; On the horizontal loaded board 9 of the riser 3 of fixed bearing 11 and fixed bearing 12, have a plurality of cooresponding strut bar mounting holes, be provided with cooresponding removable strut bar 4 and pass support rod hole and connect two fixed bearings 11,12, see Fig. 2.
Loaded board 9 is changed according to the measured piece structure is different, and the strut bar 4 that plays booster action can be for convenience detach according to the load size; Oil cylinder 2 can require the different oil cylinder working-pressures of directly regulating just can realize according to loading; 6 coaxial linking to each other of tension-compression sensor, can be according to the easy disassembly of measured piece scope.
Electric control system also is an electrical box, described electric control system comprises signal generating module, location solution mediation feedback gain adjustment module, external sensor demodulation module, pumping signal, command signal and external sensor module all adopt the high-precision microprocessor control of multidigit, have guaranteed signal accuracy and convenient the adjusting.
Microcontroller is the high-precision micro controller system of multidigit, also is circumscribed with input equipment and display equipment.
Need the outside that hydraulic efficiency power unit is provided during test system and test, the core of forming test macro is exactly test fixture and electric control system.
Fig. 4 shows the control principle of electric control system: electric control system produces control signal by microcontroller, supplies with in-to-in feedback gain adjustment module then and produces the electrohydraulic servo valve that servo current is added to measured piece, makes the start of measured piece piston; The microcontroller of leading up in addition produces pumping signal and offers measured piece in-to-in Linear displacement transducer, the displacement signal that will be directly proportional with piston inverse feedback after the demodulator circuit demodulation returns servo amplifying circuit, when servo current reduces to stop up to the measured piece piston, thereby finish the closed loop control of total system.In addition, external force gauge and Linear displacement transducer demodulation module are peripheries.
Fig. 5 is the inner microprocessor control principle of command signal and pumping signal, carry out the adjusting of the figure place and the amplitude of frequency and voltage by external input equipment push button keypad, and can control generation chopping sea, sinusoidal waveform, square wave control waveform, also can external as required control signal, and leave the output measurement point.
Fig. 6 has illustrated the flow process of external sensor data acquisition: after finishing data acquisition, the signal of importing is carried out the A/D conversion, send into microprocessor and handle the back demonstration.Equally, on the push button keypad, carry out input and output.
As shown in Figure 7, described external sensor data acquisition module comprises first microcontroller (numbering 1), two paths of data acquisition channel (numbering 2), load and displacement show (numbering 3), five parts of power supply (numbering 4) and supply terminals (numbering 5): data acquisition channel with sensor acquisition to signal give first microcontroller (STC12C5410AD), first microcontroller includes the analog to digital conversion unit, the two-way analog signal conversion can be become digital signal and through giving load after the computing and the displacement display circuit shows by the analog to digital conversion unit.
Characteristics: adopt foregoing circuit, simple in structure, data acquisition precision height (10 ADC) is fit to modularization production.Be a dapper data acquisition module, application surface is more extensive.
Shown in Fig. 8 (being the circuit diagram of Fig. 5), signal generating module is produced and adjustment module by pumping signal again, does command signal produce and adjustment module constitutes? mainly comprise: second microcontroller (numbering 6), keyboard (numbering 7), digital to analogy conversion and push-pull output circuit (numbering 8), s-f and amplitude display circuit (numbering 9) and power supply (numbering 10) and terminals (numbering 11): second microcontroller (dsPIC30F4012) is after obtaining the control signal of keyboard, the one side output data is to analogue to digital conversion and recommend output, on the other hand with data feed signals frequency and amplitude display part;
Analogue to digital conversion with recommend output and comprise two data latches 74HL373, two analog-digital chip AD7846JN, a slice amplifier LM324 and recommend output triode 5551 and 5401,74HL373 will latch from the data of microcontroller and supply with AD7846JN; Output amplitude reference voltage after a slice AD7846JN digital to analogy conversion wherein, after amplifier LM324 conversion, form positive and negative magnitude references voltage again and supply with another sheet AD7846JN, the output of another sheet AD7846 is desired signal type, and (this module can produce sine, the trigonometric sum square wave), through after the utmost point recommend and amplify back output;
S-f and amplitude display part comprise that two LED chip for driving MC14489BP and 5 highlighted LED.MC14489 obtain the microcontroller data through serial port, send LED to show the frequency and the amplitude of signal then.
Characteristics: adopt foregoing circuit, the control accuracy height, simple in structure, circuit scale is little, is fit to modularization production.Be a dapper signal generating module, application surface is more extensive.
As shown in Figure 9, the pilot control system comprises: servovalve command signal and location bias, servovalve feedback and adjusting and signal operation and three parts of driving output, during open loop control, give the command signal input control signal, deliver to the signal input and drive output with the servovalve location bias behind overregulate, servovalve drives exports to servovalve; During closed loop control, the servovalve feedback signal is reconciled the back through filtering and is given the signal input and drive output with above-mentioned two paths of signals, has introduced the servovalve feedback signal here and has formed closed loop control system.
In servovalve command signal and the location bias: order biasing (numbering 12) output forms command signal output with command signal input two paths of signals after op amp LM248N stack, and servovalve location bias (numbering 14) is the same as with order biasing (numbering 12) op amp output.
Servovalve feedback with regulate: the servovalve feedback signal forms the actv. feedback signal after through the servovalve filtering is made up of amplifier LM248N and adjusting (numbering 15) circuit, feedback signal links to each other with open/close control (numbering 16), opening/the closed loop state of switch S 201 control system, when closed loop, feedback signal is regulated the signal stack of (numbering 18) output with location bias through position amplitude adjusted (numbering 17), finally formed position signal output, simultaneously the variation tendency of VM2 needle dc voltmeter indicator signal;
During signal operation is exported with driving: the servovalve location bias, the servovalve command signal, servovalve position signal three road signals are input to signal operation and adjusting (numbering 20) circuit, give next stage servovalve gain-adjusted (numbering 21) after regulating through stack and amplification.Deliver to servovalve after the servovalve gain-adjusted again and drive (numbering 22) circuit.Servovalve drives to be made up of amplifier LM248N and pliotron, finally forms servo valve drive signal.The variation tendency of the drive signal of mAM pointer-type amperemeter/ammtr indication simultaneously.
Characteristics: adopt foregoing circuit, the control accuracy height, simple in structure, workable.It is more careful that function is divided.
Except that above-mentioned functions, can also provide command signal biasing, signal amplitude adjusting, location bias adjusting and servovalve current offset to regulate and the servo gain regulatory function.And leave all desired signal external interfaces in the test.
Claims (4)
1, a kind of test macro of plane spoiler power control assembly comprises test fixture and electric control system, it is characterized in that:
Described test fixture structure is: the fixed bearing that is provided with load oil cylinder (2) and measured piece (10) on a base plate (1) accordingly, be fixed with load oil cylinder (2) on the load oil cylinder fixed bearing (11) and pass through the coaxial continuous external force gauge (6) of adapter (5), measured piece fixed bearing (12) is for being connected the horizontal loaded board (9) on the base plate with attaching parts; Described load oil cylinder fixed bearing (11) is that horizontal riser (3) both sides are added with gusset (31) backwards, laterally having a plurality of cooresponding support rod hole on loaded board (9) and the horizontal riser (3), be provided with cooresponding removable strut bar (4) and pass support rod hole and connect two bearings; Also be provided with external displacement pickup (7) on the base plate (1);
Described electric control system comprises signal generating module, location solution mediation feedback gain adjustment module, external sensor module and pilot control system module, signal generating module and external sensor module respectively adopt the high-precision microprocessor control of multidigit, have guaranteed signal accuracy and convenient the adjusting.
2, the test macro of plane spoiler power control assembly according to claim 1, it is characterized in that: described external sensor module comprises first microcontroller (numbering 1), two paths of data acquisition channel (numbering 2), load and displacement show (numbering 3), five parts of power supply (numbering 4) and supply terminals (numbering 5): data acquisition channel with sensor acquisition to signal give first microcontroller, first microcontroller includes the analog to digital conversion unit, the two-way analog signal conversion can be become digital signal and through giving load after the computing and the displacement display circuit shows by the analog to digital conversion unit.
3, the test macro of plane spoiler power control assembly according to claim 2, it is characterized in that: described signal generating module is produced and adjustment module by pumping signal again, command signal produces and adjustment module constitutes, mainly comprise: second microcontroller (numbering 6), keyboard (numbering 7), digital to analogy conversion and push-pull output circuit (numbering 8), s-f and amplitude display circuit (numbering 9) and power supply (numbering 10) and terminals (numbering 11): second microcontroller (dsPIC30F4012) is after obtaining the control signal of keyboard, the one side output data is to analogue to digital conversion and recommend output, on the other hand with data feed signals frequency and amplitude display part;
Described analogue to digital conversion with recommend output and comprise two data latches 74HL373, two analog-digital chip AD7846JN, a slice amplifier LM324 and recommend output triode 5551 and 5401,74HL373 will latch from the data of microcontroller and supply with AD7846JN; Output amplitude reference voltage after a slice AD7846JN digital to analogy conversion wherein, after amplifier LM324 conversion, form positive and negative magnitude references voltage again and supply with another sheet AD7846JN, the output of another sheet AD7846 is desired signal type, through after the utmost point recommend and amplify back output;
Described s-f and amplitude display part comprise that two LED chip for driving MC14489BP and 5 highlighted LED.MC14489 obtain the microcontroller data through serial port, send LED to show the frequency and the amplitude of signal then.
4, the test macro of plane spoiler power control assembly according to claim 3, it is characterized in that: described pilot control system comprises: servovalve command signal and location bias, servovalve feedback and adjusting and signal operation and three parts of driving output, during open loop control, give the command signal input control signal, deliver to the signal input and drive output with the servovalve location bias behind overregulate, servovalve drives exports to servovalve; During closed loop control, the servovalve feedback signal is reconciled the back through filtering and is given the signal input and drive output with above-mentioned two paths of signals, has introduced the servovalve feedback signal here and has formed closed loop control system:
In servovalve command signal and the location bias: order biasing (numbering 12) output forms command signal output with command signal input two paths of signals after op amp LM248N stack, and servovalve location bias (numbering 14) is the same as with order biasing (numbering 12) op amp output;
Servovalve feedback with regulate: the servovalve feedback signal forms the actv. feedback signal after through the servovalve filtering is made up of amplifier LM248N and adjusting (numbering 15) circuit, feedback signal links to each other with open/close control (numbering 16), opening/the closed loop state of switch S 201 control system, when closed loop, feedback signal is regulated the signal stack of (numbering 18) output with location bias through position amplitude adjusted (numbering 17), finally formed position signal output, simultaneously the variation tendency of VM2 needle dc voltmeter indicator signal;
During signal operation is exported with driving: the servovalve location bias, the servovalve command signal, servovalve position signal three road signals are input to signal operation and adjusting (numbering 20) circuit, give next stage servovalve gain-adjusted (numbering 21) through stack and after amplifying adjusting, deliver to servovalve after the servovalve gain-adjusted again and drive (numbering 22) circuit, servovalve drives to be made up of amplifier LM248N and pliotron, the final servo valve drive signal that forms, the variation tendency of the drive signal of mAM pointer-type amperemeter/ammtr indication simultaneously.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100398130A CN101596938B (en) | 2009-05-31 | 2009-05-31 | Test system of spoiler power control unit |
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| CN2009100398130A CN101596938B (en) | 2009-05-31 | 2009-05-31 | Test system of spoiler power control unit |
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| CN101596938B CN101596938B (en) | 2013-04-17 |
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| CN2009100398130A Expired - Fee Related CN101596938B (en) | 2009-05-31 | 2009-05-31 | Test system of spoiler power control unit |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101980093A (en) * | 2010-09-29 | 2011-02-23 | 成都富凯飞机工程服务有限公司 | Airplane spoiler power control assembly testing device |
| CN102285462A (en) * | 2011-06-29 | 2011-12-21 | 南京王行航空附件维修工程有限公司 | Comprehensive test stand for aircraft pneumatic accessories |
| CN104443430A (en) * | 2014-12-12 | 2015-03-25 | 北京航星机器制造有限公司 | Test set for unfolding of folding control surface |
| CN107719679A (en) * | 2017-09-08 | 2018-02-23 | 中国飞行试验研究院 | A kind of external plane night draws lighting apparatus |
| CN110108550A (en) * | 2018-02-01 | 2019-08-09 | 株式会社岛津制作所 | Material Testing Machine |
| CN110844114A (en) * | 2019-10-15 | 2020-02-28 | 中国特种飞行器研究所 | Portable aerostat test system |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111091770A (en) * | 2019-12-17 | 2020-05-01 | 广州飞机维修工程有限公司 | Drive testing arrangement of air passenger A320 display module |
| CN113299173A (en) * | 2021-06-08 | 2021-08-24 | 无锡航试电液系统有限公司 | Nozzle demonstration oil way flow applied to aerospace |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2445938A1 (en) * | 1974-09-26 | 1976-04-29 | Dornier Gmbh | TOW FOR THE REPRESENTATION OF AIR TARGETS |
| CN201107371Y (en) * | 2007-07-20 | 2008-08-27 | 浙江豪情汽车制造有限公司 | Electric appliances durability test stand |
| CN201532315U (en) * | 2009-05-31 | 2010-07-21 | 广州飞机维修工程有限公司 | Airplane spoiler power control assembly testing system |
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2009
- 2009-05-31 CN CN2009100398130A patent/CN101596938B/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101980093A (en) * | 2010-09-29 | 2011-02-23 | 成都富凯飞机工程服务有限公司 | Airplane spoiler power control assembly testing device |
| CN101980093B (en) * | 2010-09-29 | 2012-05-30 | 成都富凯飞机工程服务有限公司 | Airplane spoiler power control assembly testing device |
| CN102285462A (en) * | 2011-06-29 | 2011-12-21 | 南京王行航空附件维修工程有限公司 | Comprehensive test stand for aircraft pneumatic accessories |
| CN104443430A (en) * | 2014-12-12 | 2015-03-25 | 北京航星机器制造有限公司 | Test set for unfolding of folding control surface |
| CN104443430B (en) * | 2014-12-12 | 2017-04-05 | 北京航星机器制造有限公司 | Fold rudder face and launch test device |
| CN107719679B (en) * | 2017-09-08 | 2019-08-06 | 中国飞行试验研究院 | A kind of external plane night traction lighting apparatus |
| CN107719679A (en) * | 2017-09-08 | 2018-02-23 | 中国飞行试验研究院 | A kind of external plane night draws lighting apparatus |
| CN110108550A (en) * | 2018-02-01 | 2019-08-09 | 株式会社岛津制作所 | Material Testing Machine |
| CN110844114A (en) * | 2019-10-15 | 2020-02-28 | 中国特种飞行器研究所 | Portable aerostat test system |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111091770A (en) * | 2019-12-17 | 2020-05-01 | 广州飞机维修工程有限公司 | Drive testing arrangement of air passenger A320 display module |
| CN111091770B (en) * | 2019-12-17 | 2024-01-05 | 广州飞机维修工程有限公司 | Drive testing device of air passenger A320 display assembly |
| CN113299173A (en) * | 2021-06-08 | 2021-08-24 | 无锡航试电液系统有限公司 | Nozzle demonstration oil way flow applied to aerospace |
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